Methods for producing forged products and other worked products are disclosed. In one embodiment, a method comprises using additive manufacturing to produce a metal shaped-preform and, after the using step, forging the metal shaped-preform into a final forged product. The final forged product may optionally be annealed.
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1. A method compromising:
(a) using additive manufacturing to produce a metal shaped-preform, wherein the metal shaped-preform comprises a titanium alloy, wherein the additive manufacturing comprises:
depositing layers of a first material on an upper side of a building substrate; and
depositing layers of a second material on a opposing lower side of the building substrate;
wherein at least one of the first material, the second material, and the building substrate comprises the titanium alloy;
(b) after the using step (a), forging the metal shaped-preform, with the building substrate therein, into a final forged product having the building substrate therein.
2. The method of
3. The method of
4. The method of
heating the metal shaped-preform to a stock temperature; and
contacting the metal shaped-preform with a forging die, wherein, when the contacting step is initiated, the forging die is a temperature that is at least 10° F. lower than the stock temperature.
6. The method of
7. The method of
9. The method of
10. The method of
after the forging step (b), annealing the final forged product.
11. The method of
12. The method of
13. The method of
prior to the using step, designing the shape of the building substrate such that, after the forging step, the building substrate is located in a predetermined area of low strain of the final forged product.
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This patent application claims priority to U.S. Provisional Patent Application No. 61/844,744, filed Jul. 10, 2013, and claims priority to U.S. Provisional Patent Application No. 61/845,260, filed Jul. 11, 2013, and claims priority to U.S. Provisional Patent Application No. 61/895,046, filed Oct. 24, 2013, and claims priority to U.S. Provisional Patent Application No. 61/913,077, filed Dec. 6, 2013, and claims priority to U.S. Provisional Patent Application No. 61/955,027, filed Mar. 18, 2014. Each of these applications is incorporated by reference in their entirety herein.
Metal products may be formed into shapes via forging operations. To forge metal products, several successive dies (flat dies and/or differently shaped dies) may be used for each part, with the flat die or the die cavity in a first of the dies being designed to deform the forging stock to a first shape defined by the configuration of that particular die, and with the next die being shaped to perform a next successive step in the forging deformation of the stock, and so on, until the final die ultimately gives the forged part a fully deformed shape. See, U.S. Pat. No. 4,055,975.
Broadly, the present patent application relates to improved methods for producing worked metal products (e.g., forged metal products; other types of hot worked and/or cold worked metal products).
In one embodiment, a method includes using additive manufacturing to produce a metal shaped-preform. After the using step, the metal shaped-preform may be forged into a final forged product. In one embodiment, the forging step comprises a single die forging step. In one embodiment, the metal preform comprises at least one of titanium, aluminum, nickel, steel, and stainless steel. In one embodiment, the metal shaped-preform may be a titanium alloy. For example, the metal shaped-preform may comprise a Ti-6Al-4V alloy. In another embodiment, the metal shaped-preform may be an aluminum alloy. In yet another embodiment, the metal shaped-preform may be a nickel alloy. In yet another embodiment, the metal shaped-preform may be one of a steel and a stainless steel. In another embodiment, the metal shaped-preform may be a metal matrix composite. In yet another embodiment, the metal shaped-preform may comprise titanium aluminide. For example, in one embodiment, the titanium alloy may include at least 48 wt. % Ti and at least one titanium aluminide phase, wherein the at least one titanium aluminide phase is selected from the group consisting of Ti3Al, TiAl and combinations thereof. In another embodiment, the titanium alloy includes at least 49 wt. % Ti. In yet another embodiment, the titanium alloy includes at least 50 wt. % Ti. In another embodiment, the titanium alloy includes 5-49 wt. % aluminum. In yet another embodiment, the titanium alloy includes 30-49 wt. % aluminum, and the titanium alloy comprises at least some TiAl. In yet another embodiment, the titanium alloy includes 5-30 wt. % aluminum, and the titanium alloy comprises at least some Ti3Al.
The forging step may comprise heating the metal shaped-preform to a stock temperature, and contacting the metal shaped-preform with a forging die. In one embodiment, when the contacting step is initiated, the forging die may be a temperature that is at least 10° F. lower than the stock temperature. In another embodiment, when the contacting step is initiated, the forging die is a temperature that is at least 25° F. lower than the stock temperature. In yet another embodiment, when the contacting step is initiated, the forging die is a temperature that is at least 50° F. lower than the stock temperature. In another embodiment, when the contacting step is initiated, the forging die is a temperature that is at least 100° F. lower than the stock temperature. In yet another embodiment, when the contacting step is initiated, the forging die is a temperature that is at least 200° F. lower than the stock temperature.
In one aspect, the final forged product is a component for an engine. In one embodiment, the final forged product is a blade for a jet engine. In another embodiment, as described below, the final forged product is an engine containment ring.
In another aspect, a method may comprise using additive manufacturing to produce a metal shaped-preform, and concomitant to, or after the using step, working the metal shaped-preform into a final worked product via at least one of: (i) rolling, (ii) ring rolling, (iii) ring forging, (iv) shaped rolling, (v) extruding, and (vi) combinations thereof. In one embodiment, the working is rolling. In another embodiment, the working is ring rolling. In yet another embodiment; the working is ring forging. In another embodiment, the working is shaped rolling. In yet another embodiment, the working is extruding.
When the metal shaped-preform comprises a Ti-6Al-4V alloy, the forging step may comprise heating the metal shaped-preform to a stock temperature, and contacting the metal shaped-preform with a forging die. In this regard, the contacting step may comprise deforming the metal shaped-preform via the forging die. In one embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of from 0.05 to 1.10 in the metal shaped-preform. In another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of at least 0.10 in the metal shaped-preform. In yet another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of at least 0.20 in the metal shaped-preform. In another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of at least 0.25 in the metal shaped-preform. In yet another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of at least 0.30 in the metal shaped-preform. In another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of at least 0.35 in the metal shaped-preform. In another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of not greater than 1.00 in the metal shaped-preform. In yet another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of not greater than 0.90 in the metal shaped-preform. In another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of not greater than 0.80 in the metal shaped-preform. In yet another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of not greater than 0.70 in the metal shaped-preform. In another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of not greater than 0.60 in the metal shaped-preform. In yet another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of not greater than 0.50 in the metal shaped-preform. In another embodiment, the contacting step comprises deforming the metal shaped-preform via the forging die to realize a true strain of not greater than 0.45 in the metal shaped-preform. As mentioned above, the forging step may comprise heating the metal shaped-preform to a stock temperature.
In one aspect, the forging step may comprise heating the metal-shaped preform to a stock temperature. In one approach, the metal shaped preform is heated to a stock temperature of from 850° C. to 978° C. In one embodiment, the metal shaped preform is heated to a stock temperature of at least 900° C. In another embodiment, the metal shaped preform is heated to a stock temperature of at least 950° C. In yet another embodiment, the metal shaped preform is heated to a stock temperature of at least 960° C. In another embodiment, the metal shaped preform is heated to a stock temperature of not greater than 975° C. In yet another embodiment, the metal shaped preform is heated to a stock temperature of not greater than 973° C.
In one aspect, the step of using additive manufacturing to produce a metal shaped-preform may comprise adding material, via additive manufacturing, to a building substrate thereby producing the metal shaped-preform. In one embodiment, the material is a first material having a first strength and wherein the building substrate is comprised of a second material having a second strength. The first material may have a first fatigue property and the second material may have a second fatigue property. For example, a layer of a first material having low strength and high toughness could be added, via additive manufacturing, to a building substrate comprised of a second material having high strength and low toughness, thereby producing a metal-shaped preform useful, for example, in ballistic applications.
In one embodiment, the building substrate comprises a first ring of a first material, and the using step comprises adding a second material, via additive manufacturing, to the first ring thereby forming a second ring, wherein the second ring is integral with the first ring.
In another aspect, the method may include, after the forging step, annealing the final forged product. In one embodiment, when the metal shaped-preform comprises a Ti-6Al-4V alloy, the annealing step may comprise heating the final forged product to a temperature of from about 640° C. to about 816° C. In another embodiment, when the metal shaped-preform comprises a Ti-6Al-4V alloy, the annealing step may comprise heating the final forged product to a temperature of from about 670° C. to about 750° C. In yet another embodiment, when the metal shaped-preform comprises a Ti-6Al-4V alloy, the annealing step may comprise heating the final forged product to a temperature of from about 700° C. to about 740° C. In another embodiment, when the metal shaped-preform comprises a Ti-6Al-4V alloy, the annealing step may comprise heating the final forged product to a temperature of about 732° C.
Reference will now be made in detail to the accompanying drawings, which at least assist in illustrating various pertinent embodiments of the new technology provided for by the present disclosure.
One embodiment of the new method for producing forged metal products is illustrated in
The additive manufacturing step (100) prepares the metal shaped-preform. Additive manufacturing, or 3-D printing, is a process where layers of a material are deposited one after another using digital printing techniques. Thus, precisely designed products can be produced. The metal shaped-preform produced by the additive manufacturing step (100) may be made from any metal suited for both additive manufacturing and forging, including, for example metals or alloys of titanium, aluminum, nickel (e.g., INCONEL), steel, and stainless steel, among others. An alloy of titanium is an alloy having titanium as the predominant alloying element. An alloy of aluminum is an alloy having aluminum as the predominant alloying element. An alloy of nickel is an alloy having nickel as the predominant alloying element. An alloy of steel is an alloy having iron as the predominant alloying element, and at least some carbon. An alloy of stainless steel is an alloy having iron as the predominant alloying element, at least some carbon, and at least some chromium. In one embodiment, the metal shaped-preform is an intermediate product in the form of a precursor to a blade for a jet engine.
Still referring to
Referring now to
In one aspect, after the forging step (200) the final forged product may optionally be annealed (300). The annealing step (300) may facilitate the relieving of residual stress in the metal-shaped preform due to the forging step (200). In one approach, the metal-shaped preform comprises a Ti-6Al-4V alloy and the annealing step (300) may comprise heating the final forged product to a temperature of from about 640° C. (1184° F.) to about 816° C. (1500° F.) and for a time of from about 0.5 hour to about 5 hours. In one embodiment, the annealing step (300) may comprise heating the final forged product to a temperature of at least about 640° C. (1184° F.). In another embodiment, the annealing step (300) may comprise heating the final forged product to a temperature of at least about 670° C. (1238° F.). In yet another embodiment, the annealing step (300) may comprise heating the final forged product to a temperature of at least about 700° C. (1292° F.). In another embodiment, the annealing step (300) may comprise heating the final forged product to a temperature of not greater than about 760° C. (1400° F.). In yet another embodiment, the annealing step (300) may comprise heating the final forged product to a temperature of not greater than about 750° C. (1382° F.). In another embodiment, the annealing step (300) may comprise heating the final forged product to a temperature of not greater than about 740° C. (1364° F.). In yet another embodiment, the time is at least about 1 hour. In another embodiment, the time is at least about 2 hours. In yet another embodiment, the time is not greater than about 4 hours. In another embodiment, the time is not greater than about 3 hours. In yet another embodiment, the annealing step (300) may comprise heating the final forged product to a temperature of about 732° C. (1350° F.) and for a time of about 2 hours.
The contacting step (220) may comprise applying a sufficient force to the metal shaped-preform via the forging die to realize a pre-selected amount of true strain in the metal shaped-preform. In one embodiment, the applying a sufficient force step comprises deforming the metal shaped-preform via the forging die. As used herein “true strain” (εtrue) is given by the formula:
εtrue=ln(L/L0)
Where L0 is initial length of the material and L is the final length of the material. In one embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of from about 0.05 to about 1.10 in the metal shaped-preform. In another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of at least 0.10 in the metal shaped-preform. In another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of at least 0.20 in the metal shaped-preform. In yet another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of at least 0.25 in the metal shaped-preform. In another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of at least 0.30 in the metal shaped-preform. In yet another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of at least 0.35 in the metal shaped-preform. In another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of not greater than 1.00 in the metal shaped-preform. In yet another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of not greater than 0.90 in the metal shaped-preform. In another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of not greater than 0.80 in the metal shaped-preform. In yet another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of not greater than 0.70 in the metal shaped-preform. In another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of not greater than 0.60 in the metal shaped-preform. In yet another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of not greater than 0.50 in the metal shaped-preform. In another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of not greater than 0.45 in the metal shaped-preform. In yet another embodiment, the contacting step (220) may comprise applying sufficient force to the metal shaped-preform via the forging die to realize a true strain of about 0.40 in the metal shaped-preform.
In one embodiment, the metal shaped-preform is a low ductility material, such as a metal matrix composite or an intermetallic material. In one embodiment, the metal shaped-preform is titanium aluminide. Using the new processes disclosed herein may facilitate more economical production of final forged products from such low ductility materials. For instance, the low ductility materials may be forged using dies and/or tooling that are at a lower temperature than the low ductility material. Thus, in one embodiment, the forging is absent of isothermal forging (i.e., the forging process does not include isothermal forging), and thus can include any of the stock temperature versus die temperature differentials noted in the above-paragraph.
In one aspect, the metal shaped preform is a titanium (Ti) alloy, and thus includes titanium as the predominant alloying element. In one embodiment, a titanium alloy includes at least 48 wt. % Ti. In another embodiment, a titanium alloy includes at least 49 wt. % Ti. In yet another embodiment, a titanium alloy includes at least 50 wt. % Ti. In one embodiment, the titanium alloy comprises one or more titanium aluminide phases. In one embodiment, the titanium aluminide phase(s) is/are one or more of Ti3Al and TiAl. When titanium aluminides are present, the titanium alloy may include 5-49 wt. % aluminum. In one embodiment, the titanium aluminide phase(s) comprise TiAl. In one embodiment, the titanium alloy includes 30-49 wt. % aluminum, and the titanium alloy comprises at least some TiAl. In one embodiment, the titanium aluminide phase(s) comprises Ti3Al. In one embodiment, the titanium alloy includes 5-30 wt. % aluminum, and the titanium alloy comprises at least some Ti3Al. In one embodiment, the titanium alloy comprises aluminum and vanadium.
In one embodiment, the metal shaped preform comprises a Ti-6Al-4V alloy (a titanium alloy having about 6 wt. % aluminum and about 4 wt. % vanadium). In this regard, the Ti-6Al-4V preforms may be heated to a stock temperature of from about 850° C. (1562° F.) to about 978° C. (1792° F.). In one embodiment, the Ti-6Al-4V preforms may be heated to a stock temperature of at least 900° C. (1652° F.). In another embodiment, the Ti-6Al-4V preforms may be heated to a stock temperature of at least 925° C. (1697° F.). In another embodiment, the Ti-6Al-4V preforms may be heated to a stock temperature of at least 950° C. (1742° F.). In yet another embodiment, the Ti-6Al-4V preforms may be heated to a stock temperature of at least 960° C. (1760° F.). In another embodiment, the Ti-6Al-4V preforms may be heated to a stock temperature of not greater than 975° C. (1787° F.). In yet another embodiment, the Ti-6Al-4V preforms may be heated to a stock temperature of not greater than 973° C. (1783° F.).
The final forged product may be used in the aerospace, aviation, or medical industries, for example. The final forged product could be, for example, a turbine or blade. In one embodiment, the final forged product is a blade for a jet engine.
As mentioned above, after the additive manufacturing step (100), the metal shaped-preform may be forged (200) to create a final forged product. In other embodiments, after the additive manufacturing step (100), the metal shaped-preform may be processed via other forms of working (e.g., hot working) to create a final worked product. For instance, the working of the metal shaped-preform may also or alternatively include rolling, ring rolling, ring forging, shaped rolling, and/or extruding to create the final worked product. In some embodiments, the final worked product may realize improved properties, such as improved porosity (e.g., less porosity), improved surface roughness (e.g., less surface roughness, i.e., a smoother surface), and/or better mechanical properties (e.g., improved surface hardness), among others. In some embodiments, the final worked product may realize a predetermined shape. In some embodiments, the metal shaped-preform may be ring rolled, ring forged and/or extruded (e.g., forced through a die) to create a hollow final worked product. In some embodiments, the metal shaped-preform may be rolled to produce a final worked product that realizes improved porosity. In some embodiments, the metal shaped-preform may be shape rolled to produce a final worked product that realizes a predetermined shape (e.g., a curve having a specified radius).
As used herein, “ring rolling” means the process of rolling a ring of smaller diameter (e.g., a first ring having a first diameter) into a ring of larger diameter (e.g, a second ring having a second diameter, wherein the second diameter is larger than the first diameter), optionally with a modified cross section (e.g., a cross sectional area of the second ring is different than a cross sectional area of the first ring) by the use of two rotating rollers, one placed in the inside diameter of the ring and the second directly opposite the first on the outside diameter of the ring. As used herein, “ring forging” means the process of forging a ring of smaller diameter (e.g., a first ring having a first diameter) into a ring of larger diameter (e.g, a second ring having a second diameter, wherein the second diameter is larger than the first diameter), optionally with a modified cross section (e.g., a cross sectional area of the second ring is different than a cross sectional area of the first ring) by squeezing the ring between two tools or dies, one on the inside diameter and one directly opposite on the outside diameter of the ring. As used herein, “shaped rolling” means the process of shaping or forming by working the piece (i.e., the metal shaped-preform) between two or more rollers, which may or may not be profiled, to impart a curvature or shape to the work piece (i.e., the metal shaped-preform).
The step of preparing the metal shaped-preform via additive manufacturing (100) may include incorporating a building substrate into the metal shaped-preform. Referring now to
As mentioned above, a final forged product may realize an amount (e.g., a pre-selected amount) of true strain due to the contacting step 220. In some embodiments, the strain realized by the final forged product may be non-uniform throughout the final forged product due to, for example, the shape of the forging dies and/or the shape of the metal shaped-preform. Thus, the final forged product may realize areas of low and/or high strain. Accordingly, the building substrate may be located in a predetermined area of the metal shaped-preform such that after the forging, the building substrate is located in a predetermined area of low strain of the final forged product. An area of low strain may be predetermined based on predictive modeling or empirical testing.
Referring now to
The building substrate may have a predetermined shape and/or predetermined mechanical properties (e.g., strength, toughness to name a few). In one embodiment, the building substrate may be a pre-wrought base plate. In one embodiment, the shape of the building substrate may be predetermined based on the shape of the area of low strain. In one embodiment, the mechanical properties of the building substrate may be predetermined based on the average true strain realized by the metal shaped-preform and/or the true strain realized within the area of low strain. In one embodiment, two or more building substrates may be incorporated into a metal-shaped preform. In one embodiment, the building substrate comprises a pre-wrought base plate.
The building substrate may be made from any metal suited for both additive manufacturing and forging, including, for example metals or alloys of titanium, aluminum, nickel (e.g., INCONEL), steel, and stainless steel, among others. In one embodiment, the building substrate is made of the same material(s) as the rest of the metal-shaped preform. In one embodiment, the material added to the metal shaped preform may be a first material, whereas the building substrate may be made of a second material. In one embodiment, the first material may have a first strength and the second material may have a second strength. In one embodiment, the first material may have a first fatigue property and the second material may have a second fatigue property. In one example, the building substrate may be a first ring of a first material. A second material may be added, via additive manufacturing, to the ring thereby forming a second ring of the second material, integral with the first ring. Thus a ring-shaped metal shaped-preform comprising two different materials may be produced. The ring-shaped metal shaped-preform may then be forged into a ring-shaped final forged product comprising two different materials. In one embodiment, one or more engine containment rings (e.g., one or more aerospace engine containment rings) may be formed by the method described above. For example the building substrate may comprise a first ring of a material which realizes high toughness. A second ring of a second material which realizes high strength may be added, via additive manufacturing, to the first ring thereby forming a metal shaped-preform. The metal shaped-preform may then be forged into an engine containment ring having an inner ring of high toughness and outer ring of high strength.
Several Ti-6Al-4V preforms are produced via additive manufacturing. Specifically cylindrical Ti-6Al-4V preforms were produced via an EOSINT M 280 Direct Metal Laser Sintering (DMLS) additive manufacturing system, available from EOS GmbH (Robert-Stirling-Ring 1, 82152 Krailling/Munich, Germany). The Ti-6Al-4V preforms were produced in accordance with the manufacturer's standard recommended operating conditions for titanium. The preforms were then heated to a stock temperature of about 958° C. (1756° F.) or about 972° C. (1782° F.). Next, some of the cylindrical preforms were forged under various amounts of true strain and using a die temperature of about 390° C.-400° C. (734° F.-752° F.) to produce cylindrical final forged products. The true strain was applied to the cylindrical preforms in a direction parallel to the axis of the cylinders. The remaining preforms were left unforged. Some of the final forged products were then annealed at a temperature of about 732° C. (1350° F.) for approximately two hours to produce annealed final forged products. Mechanical properties of the unforged preforms, the final forged products, and the annealed final forged products were then tested, including tensile yield strength (TYS), ultimate tensile strength (UTS) and elongation, all in the L direction, the results of which are shown in
As shown, the forged Ti-6Al-4V products achieved improved properties over the unforged Ti-6Al-4V preforms. Specifically, and with reference to
Furthermore, the annealed final forged products achieved improved properties over the final forged products which were not annealed. Specifically, and with reference to
While various embodiments of the present disclosure have been described in detail, it is apparent that modification and adaptations of those embodiments will occur to those skilled in the art. However, it is to be expressly understood that such modifications and adaptations are within the spirit and scope of the present disclosure.
Colvin, Edward L., Rioja, Roberto J., Bush, Dustin M., Roegner, Eric V., Mueller, Larry N., Bodily, Brandon Hendrickson
Patent | Priority | Assignee | Title |
10513076, | Jun 06 2017 | CONNECTING PRODUCTS, INC | 3D printing devices and methods |
11554443, | Jan 14 2016 | HOWMET AEROSPACE INC | Methods for producing forged products and other worked products |
Patent | Priority | Assignee | Title |
4055975, | Apr 01 1977 | Lockheed Aircraft Corporation | Precision forging of titanium |
4294615, | Jul 25 1979 | United Technologies Corporation | Titanium alloys of the TiAl type |
5102451, | Nov 08 1990 | Dynamet Technology, Inc. | Titanium aluminide/titanium alloy microcomposite material |
5622216, | Nov 22 1994 | SEMI-SOLID TECHNOLOGIES, INC | Method and apparatus for metal solid freeform fabrication utilizing partially solidified metal slurry |
6127044, | Sep 13 1995 | Kabushiki Kaisha Toshiba; Boehler Schmiedetechnik Gesellschaft mit beschrankter Haftung & Company | Method for producing titanium alloy turbine blades and titanium alloy turbine blades |
6519500, | Sep 16 1999 | Solidica, Inc. | Ultrasonic object consolidation |
7087109, | Sep 25 2002 | 3D Systems, Inc | Three dimensional printing material system and method |
8017070, | May 17 2007 | The Boeing Company | Direct to metal sintering of 17-4PH steel |
8240046, | Mar 24 2009 | General Electric Company | Methods for making near net shape airfoil leading edge protection |
8394168, | Jan 31 2005 | ATS MER, LLC | Low cost process for the manufacture of near net shape titanium bodies |
20040084118, | |||
20040244887, | |||
20060065330, | |||
20070023975, | |||
20070089815, | |||
20070118243, | |||
20100242843, | |||
20100279007, | |||
20100291401, | |||
20110042859, | |||
20110097213, | |||
20110135952, | |||
20110183030, | |||
20110241947, | |||
20130039799, | |||
20130071562, | |||
WO2010049696, | |||
WO2012065729, | |||
WO2013087515, |
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